Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/12—Blades
  • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
  • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
  • B29B11/00—Making preforms
  • B29B11/14—Making preforms characterised by structure or composition
  • B29B11/16—Making preforms characterised by structure or composition comprising fillers or reinforcement
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
  • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
  • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
  • B29C70/06—Fibrous reinforcements only
  • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
  • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
  • B29C70/22—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
  • B29C70/222—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure the structure being shaped to form a three dimensional configuration
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
  • B29D99/00—Subject matter not provided for in other groups of this subclass
  • B29D99/0025—Producing blades or the like, e.g. blades for turbines, propellers, or wings
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/12—Blades
  • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/12—Blades
  • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
  • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
  • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
  • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
  • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
  • B29C70/06—Fibrous reinforcements only
  • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
  • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
  • B29C70/24—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
  • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
  • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
  • B29C70/28—Shaping operations therefor
  • B29C70/40—Shaping or impregnating by compression not applied
  • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
  • B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
  • B29C70/48—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
  • B29K2307/00—Use of elements other than metals as reinforcement
  • B29K2307/04—Carbon
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
  • B29L2031/00—Other particular articles
  • B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2220/00—Application
  • F05D2220/30—Application in turbines
  • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2230/00—Manufacture
  • F05D2230/50—Building or constructing in particular ways
  • F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2240/00—Components
  • F05D2240/20—Rotors
  • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
  • F05D2300/603—Composites; e.g. fibre-reinforced
  • F05D2300/6034—Orientation of fibres, weaving, ply angle
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

• the present disclosure relates to a preform for a turbomachine blade and a monobloc blade that can be formed by means of such a preform, a bladed wheel and a turbomachine comprising such a blade.
• Such a preform can be used to make blades comprising aerodynamic platforms provided with retaining legs.
• Such vanes may be including fan blades of an aircraft turbojet engine, to cite only this example.
• these platforms must meet a large number of requirements and perform many functions. Mainly, such platforms must provide an aerodynamic function of defining and channeling the flow of air flow in the turbojet engine. However, they must also ensure a guaranteed mechanical strength for all phases of flight and a consistent integration into the engine environment by avoiding in particular introducing disturbances in the downstream air vein. Thus, the geometry of the platforms must be finely controlled, and this throughout the operation of the engine, and whatever the phase of the flight.
• these platforms have in operation irregularities of shape likely to disturb the air flow and thus the efficiency of the turbomachine.
• the sag is dependent, inter alia, on the length of the cantilever.
• the cantilever being different between the upper and lower surfaces of two consecutive blades, this results in a discontinuity of sagging at this interface and a risk of overlapping platforms.
• the present disclosure relates to a preform for a turbomachine blade, obtained by three-dimensional weaving, comprising a first longitudinal section, capable of forming at least a portion of a blade root, a second longitudinal section, extending upward the first section longitudinal, able to form at least a portion of a stilt, a third longitudinal section, extending upwardly the second longitudinal section, capable of forming a portion of blade, a first transverse section extending transversely from the junction between the second and third longitudinal sections, able to form a first platform, and a first oblique section, extending from the junction between the first and second longitudinal sections to the first transverse section, capable of forming a retaining leg for the first platform .
• a blade comprising a blade root, a stilt, a portion of blade and at least one platform provided with a retaining leg for retaining the platform against the centrifugal force at during the operation of the turbomachine. This stiffens the platform and reduces its deformations in operation.
• the centrifugal forces exerted on the platform are taken up by the retaining leg and transmitted to the foot or stilt of the dawn which are structural parts of the dawn.
• the platform and the retaining leg thus form a kind of box which reduces the importance of the cantilever of the platform. Therefore, the platform maintains in operation a relatively regular profile, not disturbing or little movement of the air stream.
• this configuration also reduces the discontinuity usually observed in operation at the interface between neighboring platforms.
• the retaining leg also reduces the risk of overlap of a platform on the neighboring platform, in case of ingestion of bird for example.
• the terms “longitudinal”, “transversal”, “lower”, “superior” and their derivatives are defined in relation to the principal direction of the dawn under consideration, with the blade root being located on the lower side of dawn according to this reference; the terms “proximal”, “distal” and their derivatives are defined with respect to the blade of dawn; the terms “axial”, “radial”, “tangential” and their derivatives are themselves defined with respect to the main axis of the wheel comprising these blades, that is to say in general the axis of the turbomachine .
• axial plane means a plane passing through the main axis of the turbomachine and "radial plane” a plane perpendicular to this main axis;
• longitudinal plane a plane parallel to the main direction of the blade and perpendicular to the direction of extension of the blade root: such a longitudinal plane is a radial plane in the reference system of the turbomachine.
• upstream and downstream are defined relative to the flow of air in the turbomachine.
• three-dimensional weaving is understood to mean a weaving technique in which weft threads circulate within a matrix of warp yarns so as to form a three-dimensional network of yarns according to a three-dimensional weave: all the layers of yarns of such a fibrous structure are then woven during the same weaving step within a three-dimensional weaving loom.
• the first oblique section is continuous from the upstream end to the downstream end of the preform.
• the platform is thus retained along its entire length, which reduces its deformations more effectively.
• the first oblique section comprises a plurality of tabs distributed from upstream to downstream. This configuration reduces the mass of the preform and thus the final dawn. It also facilitates the release of the dawn after consolidation of the preform.
• the distal end of the first oblique section runs along the distal end of the first transverse section. In this way, the centrifugal forces are taken up at the platform where they are the most important, that is to say where the platform has the largest offset relative to the blade portion.
• the distal end of the first oblique section is attached to the first transverse section. This facilitates the shaping of the preform for consolidation to result in a final blade in which the platform and the retaining leg are secured.
• This attachment can be achieved by any fastening means, for example by sewing, gluing, riveting or broaching.
• the first oblique section is substantially planar. This facilitates the transmission of efforts to the foot or stilt of dawn.
• the first longitudinal portion has a substantially constant length from the upstream end to the downstream end of the preform. This facilitates the realization of the debonding at the origin of the separation of the second longitudinal section and the first oblique section.
• the length of the second longitudinal section increases from the upstream end of the preform to its downstream end. This is particularly useful in the case of a fan blade to ensure the continuity of the air stream between the upstream ferrule, of small diameter, and the downstream drum, of greater diameter.
• the fiber preform comprises a second transverse section, extending transversely from the junction between the second and third longitudinal sections, in the extension and opposite the first transverse section, capable of forming a second platform, and the preform further comprises a second oblique section, extending from the junction between the first and second longitudinal sections to the second transverse section, adapted to form a retaining leg for the second platform.
• the fibrous preform comprises only one transverse section and one oblique section.
• the final dawn has a single platform adapted to extend until the next dawn, which increases the regularity of the air vein between two neighboring blades.
• the platform is preferably provided on the extrados side: this facilitates shaping and demolding of the blade after consolidation of the preform.
• the preform comprises an interface element provided at the junction between the second and third longitudinal sections on its surface opposite to the first transverse section.
• This interface element makes it possible to cooperate with the coincident platform of the neighboring dawn. Depending on its configuration, it can protect the blade from this preform in case of impact with the next dawn, in case of bird ingestion for example, and / or block the position of the platform of the neighboring dawn against centrifugal forces.
• the interface element is a reported metal strip. This band may for example be fixed on the preform before co-injection with the latter.
• the interface element is a reported metal strip. In some embodiments, the interface element is a woven strip extending from the junction between the second and third longitudinal sections.
• the yarns used for weaving the preform are carbon fibers. However, it can be any other type of yarn, for example fiberglass or Kevlar.
• the weave used for three-dimensional weaving of the preform is of the 3D interlock type.
• the weaving of the outer surfaces of the preform can be essentially two-dimensional, of the satin type for example.
• the present disclosure also relates to a blade for a turbomachine, comprising a blade root, a stilt, extending upwards from the blade root, a portion of blade, extending upwards from the stilt, a platform, extending transversely to the blade portion at the junction between the stilt and the blade portion, and a retaining leg, extending between the foot or the stilt on the one hand and the platform of the blade 'somewhere else.
• this blade corresponds to that which can be obtained using the preform above.
• a blade could also be obtained using another process and made of another material: such a blade could for example be made of metal using a suitable foundry process. In either case, all the features and advantages described above are directly transposed to this dawn, whatever its technique of obtaining.
• the blade is made integrally of a composite material by means of a preform according to any one of the preceding embodiments, said preform having been shaped in a mold and embedded in a matrix.
• the matrix is of organic type. It may especially be an epoxy resin.
• the present disclosure also relates to a bladed wheel for a turbomachine, comprising a plurality of blades according to one of the preceding embodiments.
• It may be a rotor wheel, such as a fan, in which the vanes are angularly disposed around a rotating hub, or a stator wheel, in which the vanes are arranged angularly within a rotor. fixed ferrule.
• the present disclosure also relates to a turbomachine, comprising at least one blade or a bladed wheel according to one of the preceding embodiments.
• FIG 1 is a plane in axial section of a turbomachine according to the invention.
• FIG 2 is a partial diagram in radial section of a bladed wheel according to the invention.
• FIG 3 is a partial perspective view of a blade according to an exemplary embodiment.
• FIG 4 is a partial view of the blade of FIG 3 in perspective from another angle.
• FIG 5 schematically illustrates the preform corresponding to this example of blade before shaping.
• FIG 6 schematically illustrates the preform corresponding to this example of blade after shaping.
• FIG 7A schematically illustrates a second example of preform before shaping.
• FIG 7B schematically illustrates the preform of this second example after its shaping.
• FIG 1 shows, in section along a vertical plane passing through its main axis A, a turbofan engine 1 according to the invention. It comprises, from upstream to downstream according to the flow of the air flow, a fan 2, a low pressure compressor 3, a high pressure compressor 4, a combustion chamber 5, a high pressure turbine 6, and a low pressure turbine 7.
• the fan 2 is provided with a plurality of fan blades 10 mounted angularly about the axis A on a disk 11 connected to the low-pressure shaft of the turbomachine 1.
• Such a fan blade is shown in FIGS. 3 and 4. It comprises a dovetail blade root 21 configured to engage a groove 12 of the disk 11 in order to fix it to the disk 11.
• This blade root 21 is extended upwards by a staggered 22 then by a blade 23 having an extrados face 23e and a face intrados 23i each upstream upstream between a leading edge 23a and a trailing edge 23f.
• the blade 10 further comprises an extrados platform 24, extending transversely on the extrados side of the blade from the junction between the stilt 22 and the blade 23, and an intrados platform 25, extending transversely on the lower surface of the blade. dawn from the junction between the stilt 22 and the blade 23.
• the blade 10 further comprises an extrados retaining leg 26, extending from the junction between the blade root 21 and the stalk 22 to the distal end of the extrados platform 24, and similarly , an intrados retaining leg 27, extending from the junction between the blade root 21 and the stalk 22 to the distal end of the intrados platform 25.
• each platform 24, 25 forms with its retaining leg 26, 27 and stag 22 a hollow box 29 having a substantially triangular profile.
• the junction zone between the blade root 21 and the stilt 22 is provided at a substantially constant height along the blade 10 from upstream to downstream.
• the height of the stilt 22 increases from upstream to downstream so that the boxes 29 have a funnel-shaped opening towards the downstream side of the blade 10.
• the blade 10 is obtained in a monobloc manner by 3D weaving of a fiber preform 30, shaping of this preform 30 and injection of an organic resin according to the RTM method known to those skilled in the art.
• FIG 5 shows the blank 30 'woven three-dimensionally of this preform 30 to achieve this example of blade 10.
• FIG 6 represents the final preform 30 after cutting and shaping this blank 30'.
• This blank preform 30 ' will be described from bottom to top, that is to say from upstream downstream in the weaving direction T. However, it goes without saying that weaving could be done from the other end and in the other direction.
• the preform 30 is woven three-dimensionally in carbon fibers in 3D interlock armor. Only the surfaces of the preform 30 are woven two-dimensionally in a satin-like weave.
• weaving begins with the production of a first longitudinal section 31 which will form the root 21 of the blade 10.
• first longitudinal section 31 starts a first debonding zone D1 in which a first free flange 36a, a second longitudinal section 32 and a second free flange 37a are loosely woven together with deflection planes 38.
• first and second free sides preferably have a thickness of two or three layers of son, a thickness of about 2 or 3 mm.
• This first zone of debonding can begin at any height of the future stilt.
• second longitudinal section 32 begins a second deliming zone D2 in which the continuation of the first free pan 36a, a third free pan 34a, a third longitudinal section 33, a fourth free pan 35a and the continuation of the second free pan. 37a are loosely woven together with two new debonding planes 39 in addition to the first debonding planes 38 which extend.
• the third and fourth free sides 34a and 35a are cut so as to form a first transverse section 34, which will form the extrados platform 24 of the blade 10, and a second transverse section 35, which will form the platform intrados 25 of the dawn 10.
• the first and second free faces 36a and 37a are also cut to form a first oblique section 36, which will form the extrados retaining leg 26 of the blade 10, and a second oblique section 37, which will form the retaining leg 27. of dawn 10.
• the blank 30 ' can then be wetted to soften it and allow easier decadding of the fibers.
• the blank 30 ' is then introduced into a forming mold whose interior space is adjusted to the desired geometry for the preform 30.
• each oblique section 36, 37 then extends along the distal end of the corresponding transverse section 34, 35. The ends of these sections can then be sewn together to secure them.
• the preform 30 thus shaped is finally disposed in an injection mold, to the dimensions of the desired final blade 10. Inserts are further inserted into the boxes formed by the transverse sections 34, 35 and oblique 36, 37 so to maintain the shape of the latter and to prevent the matrix from filling the internal volume of these boxes.
• the matrix is then injected, here an epoxy resin.
• RTM resin transfer molding
• weaving example described above is only one of many other possible examples that those skilled in the art will readily recognize.
• other delimitations or to use other weaving techniques such as cross-layers, layer outlets or thickness transitions to obtain a similar preform geometry.
• Those skilled in the art will find in particular many examples of weavings in the document WO 2014/076408.
• first and second free faces 36a and 37a are cut in certain places to the junction zone between the first and second longitudinal sections.
• the oblique sections 36, 37 obtained are actually formed of a plurality of tabs spaced from each other.
• FIGS. 7A and 7B illustrate a second example of preform 130.
• the preform 130 comprises only one transverse section 134 and a single oblique section 136 provided on the extrados side.
• the dawn resulting from such a preform 130 thus has only one platform, provided on its extrados side. This platform and its retaining leg are therefore longer to fill the entire space between two consecutive blades in the blower.
• the method of weaving the blank 130 'of this preform 130 is quite similar to that of the first example except that only the first and third free sides 136a, 134a are loosely woven with the sections longitudinal members 132 and 133 of the blank 130 '.
• these free planes 134a and 136a are cut at a greater height to provide the transverse sections 134 and oblique 136 of greater length.
• a metal strip 141 is attached all along the preform 130 at the junction between the second and third longitudinal sections 132, 133, on the opposite side to the transverse section 134. During the injection of the matrix, this metal band 141 is then trapped on the surface of the dawn and forms and an interface element adapted to cooperate with the distal end of the platform of a neighboring blade.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Materials Engineering (AREA)
• Composite Materials (AREA)
• Textile Engineering (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)
• Moulding By Coating Moulds (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Woven Fabrics (AREA)

Applications Claiming Priority (2)

Publications (2)

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Family Applications (1)

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• 2015
  • 2015-04-29 FR FR1553851A patent/FR3035678B1/fr not_active Expired - Fee Related
• 2016
  • 2016-04-26 BR BR112017023163-8A patent/BR112017023163B1/pt active IP Right Grant
  • 2016-04-26 CN CN201680024872.9A patent/CN107530909B/zh active Active
  • 2016-04-26 US US15/569,134 patent/US10619493B2/en active Active
  • 2016-04-26 RU RU2017141278A patent/RU2701534C2/ru active
  • 2016-04-26 EP EP16722314.8A patent/EP3288738B1/de active Active
  • 2016-04-26 CA CA2983970A patent/CA2983970C/fr active Active
  • 2016-04-26 WO PCT/FR2016/050982 patent/WO2016174346A1/fr active Application Filing
  • 2016-04-26 JP JP2017556610A patent/JP6771488B2/ja active Active

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